EP1193450A1 - Mischvorrichtung mit mehreren Verwirbelungsvorrichtungen - Google Patents
Mischvorrichtung mit mehreren Verwirbelungsvorrichtungen Download PDFInfo
- Publication number
- EP1193450A1 EP1193450A1 EP01308241A EP01308241A EP1193450A1 EP 1193450 A1 EP1193450 A1 EP 1193450A1 EP 01308241 A EP01308241 A EP 01308241A EP 01308241 A EP01308241 A EP 01308241A EP 1193450 A1 EP1193450 A1 EP 1193450A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- fuel
- mixer
- pilot
- swirlers
- housing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/34—Feeding into different combustion zones
- F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
- F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
- F23D2900/00015—Pilot burners specially adapted for low load or transient conditions, e.g. for increasing stability
Definitions
- the present invention relates generally to gas turbine engine combustors, and more particularly to a combustor including a mixer having multiple injectors.
- Fuel and air are mixed and burned in combustors of aircraft engines to heat flowpath gases.
- the combustors include an outer liner and an inner liner defining an annular combustion chamber in which the fuel and air are mixed and burned.
- a dome mounted at the upstream end of the combustion chamber includes mixers for mixing fuel and air. Ignitors mounted downstream from the mixers ignite the mixture so it burns in the combustion chamber.
- NOx nitrogen oxides
- HC unburned hydrocarbons
- CO carbon monoxide
- Some prior art combustors such as rich dome combustors 10 as shown in Fig. 1 have mixers 12 which provide a rich fuel-to-air ratio adjacent an upstream end 14 of the combustor. Because additional air is added through dilution holes 16 in the combustor 10, the fuel-to-air ratio is lean at a downstream end 18 of a combustor opposite the upstream end 14.
- combustor designers have increased the operating pressure ratio of the gas turbine engines. However, as the operating pressure ratios increase, the combustor temperatures increase. Eventually the temperatures and pressures reach a threshold at which the fuel-air reaction occurs much faster than mixing. This results in local hot spots and increased NOx emissions.
- Lean dome combustors 20 as shown in Fig. 2 have the potential to prevent local hot spots. These combustors 20 have two rows of mixers 22, 24 allowing the combustor to be tuned for operation at different conditions.
- the outer row of mixers 24 is designed to operate efficiently at idle conditions. At higher power settings such as takeoff and cruise, both rows of mixers 22, 24 are used, although the majority of fuel and air are supplied to the inner row of mixers.
- the inner mixers 22 are designed to operate most efficiently with lower NOx emissions at high power settings. Although the inner and outer mixers 22, 24 are optimally tuned, the regions between the mixers may have cold spots which produce increased HC and CO emissions.
- the assembly includes a pilot mixer and a main mixer.
- the pilot mixer includes an annular pilot housing having a hollow interior, a pilot fuel nozzle mounted in the housing and adapted for dispensing droplets of fuel to the hollow interior of the pilot housing, and one or more axial swirlers positioned upstream from the pilot fuel nozzle.
- Each of the pilot mixer swirlers has a plurality of vanes for swirling air traveling through the swirler to mix air and the droplets of fuel dispensed by the pilot fuel nozzle.
- the main mixer includes a main housing surrounding the pilot housing and defining an annular cavity, an annular fuel injector having a plurality of fuel injection ports arranged in a circular pattern surrounding the pilot housing and mounted inside the annular cavity of the main mixer for releasing droplets of fuel into swirling air downstream from the fuel injector, and one or more axial swirlers positioned upstream from the plurality of fuel injection ports.
- Each of the main mixer swirlers has a plurality of vanes for swirling air traveling through the swirler to mix air and the droplets of fuel dispensed by the fuel injection ports.
- the mixer assembly of the present invention includes a main mixer having a plurality of swirlers positioned upstream from the plurality of fuel injection ports.
- Each of the main mixer swirlers has a plurality of vanes for swirling air traveling through the respective swirler to mix air and the droplets of fuel dispensed by the fuel injection ports.
- a combustor of the present invention is designated in its entirety by the reference number 30.
- the combustor 30 has a combustion chamber 32 in which combustor air is mixed with fuel and burned.
- the combustor 30 includes an outer liner 34 and an inner liner 36.
- the outer liner 34 defines an outer boundary of the combustion chamber 32, and the inner liner 36 defines an inner boundary of the combustion chamber.
- An annular dome, generally designated by 38, mounted upstream from the outer liner 34 and the inner liner 36 defines an upstream end of the combustion chamber 32.
- Mixer assemblies or mixers of the present invention, generally designated by 50 are positioned on the dome 38.
- the mixer assemblies 50 deliver a mixture of fuel and air to the combustion chamber 32.
- Other features of the combustion chamber 30 are conventional and will not be discussed in further detail.
- each mixer assembly 50 generally comprises a pilot mixer, generally designated by 52, and a main mixer, generally designated by 54, surrounding the pilot mixer.
- the pilot mixer 52 includes an annular pilot housing 60 having a hollow interior 62.
- a pilot fuel nozzle, generally designated by 64, is mounted in the housing 60 along a centerline 66 of the mixer 50.
- the nozzle 64 includes a fuel injector 68 adapted for dispensing droplets of fuel into the hollow interior 62 of the pilot housing 60. It is envisioned that the fuel injector 68 may include an injector such as described in U.S. Patent No. 5,435,884, which is hereby incorporated by reference.
- the pilot mixer 52 also includes a pair of concentrically mounted axial swirlers, generally designated by 70, 72, having a plurality of vanes 74, 76, respectively, positioned upstream from the pilot fuel nozzle 64.
- the swirlers 70, 72 may have different numbers of vanes 74, 76 without departing from the scope of the present invention, in one embodiment the inner pilot swirler has 10 vanes and the outer pilot swirler has 10 vanes.
- Each of the vanes 74, 76 is skewed relative to the centerline 66 of the mixer 50 for swirling air traveling through the pilot mixer 52 so it mixes with the droplets of fuel dispensed by the pilot fuel nozzle 64 to form a fuel-air mixture selected for optimal burning during ignition and low power settings of the engine.
- pilot mixer 52 of the disclosed embodiment has two axial swirlers 70, 72, those skilled in the art will appreciate that the mixer may include more swirlers without departing from the scope of the present invention.
- the swirlers 70, 72 may be configured alternatively to swirl air in the same direction or in opposite directions.
- the pilot interior 62 may be sized and the pilot inner and outer swirler 70, 72 airflows and swirl angles may be selected to provide good ignition characteristics, lean stability and low CO and HC emissions at low power conditions.
- a cylindrical barrier 78 is positioned between the swirlers 70, 72 for separating airflow traveling through the inner swirler 70 from that flowing through the outer swirler 72.
- the barrier 78 has a converging-diverging inner surface 80 which provides a fuel filming surface to aid in low power performance.
- the housing 60 has a generally diverging inner surface 82 adapted to provide controlled diffusion for mixing the pilot air with the main mixer airflow. The diffusion also reduces the axial velocities of air passing through the pilot mixer 52 and allows recirculation of hot gasses to stabilize the pilot flame.
- the main mixer 54 includes a main housing, generally designated by 90, comprising an inner shell 92 and an outer shell 94 surrounding the pilot housing 60 so the housing defines an annular cavity 96.
- the inner shell 92 and outer shell 94 converge to provide thorough mixing without auto-ignition.
- An annular fuel injector, generally designated by 100 is mounted between the pilot inner shell 92 and the outer shell 94.
- the injector 100 has a plurality of outward facing fuel injection ports 102 on its exterior surface 104 and a plurality of inward facing fuel injection ports 106 on its interior surface 108 for introducing fuel into the cavity 96 of the main mixer 54.
- the injector 100 may have a different number of ports 102, 106 without departing from the scope of the present invention, in one embodiment the injector 100 has 20 evenly spaced outward facing ports 102 and 20 evenly spaced ports inward facing ports 106.
- each set of ports 102, 106 is arranged in a single circumferential row in the embodiment shown in Fig. 4, those skilled in the art will appreciate that they may be arranged in other configurations (e.g., in multiple rows) without departing from the scope of the present invention.
- using two rows of fuel injector ports 102, 106 at different radial locations in the main mixer cavity 96 provides flexibility to adjust the degree of fuel-air mixing to achieve low NOx and complete combustion under variable conditions.
- the large number of fuel injection ports in each row provides for good circumferential fuel-air mixing.
- the different radial locations of the rows may be selected to prevent combustion instability.
- the fuel injection ports 102, 106 may be fed by independent fuel stages to achieve improved fuel/air ratios.
- the inward facing ports 106 would be fueled during approach and cruise conditions. It is expected that this would significantly improve both NOx and combustion efficiency at these conditions compared to current technology.
- the outward facing ports 102 would only be fueled during takeoff.
- the fuel ports 102, 106 may be plain jets or sprayers without departing from the scope of the present invention.
- the main mixer 54 also includes three concentrically mounted axial swirlers, generally designated by 110,112,114, having a plurality of vanes 116, 118, 120 respectively, positioned upstream from the main mixer fuel injector 100.
- the swirlers may have different numbers of vanes 116, 118, 120 without departing from the scope of the present invention, in one embodiment the inner main swirler 110 has 20 vanes, the middle main swirler 112 has 24 vanes, and the outer main swirler 114 has 28 vanes.
- Each of the vanes 116, 118, 120 is skewed relative to the centerline 66 of the mixer 50 for swirling air traveling through the main mixer 54 so it mixes with the droplets of fuel dispensed by the main fuel injector 100 to form a fuel-air mixture selected for optimal burning during high power settings of the engine.
- the main mixer 54 of the disclosed embodiment has three axial swirlers 110, 112, 114, those skilled in the art will appreciate that the mixer may include a different number of swirlers without departing from the scope of the present invention.
- the main mixer 54 is primarily designed to achieve low NOx under high power conditions by operating with a lean air-fuel mixture and by maximizing the fuel and air pre-mixing.
- the swirlers 110, 112, 114 of the main mixer 54 may have other configurations without departing from scope the present invention, in one embodiment the swirlers of the main mixer and the swirlers 70, 72 of the pilot mixer 52 are aligned in a single plane.
- the axial swirlers 70, 72, 110, 112, 114 of the present invention provide better discharge coefficients than radial swirlers.
- the axial swirlers provide required airflow in a smaller area than radial swirlers and therefore minimize mixer area.
- the swirlers 110, 112, 114 of the main mixer 54 swirl the incoming air and establish the basic flow field of the combustor 30. Fuel is injected radially inward and outward into the swirling air stream downstream from the main swirlers 110, 112, 114 allowing for thorough mixing within the main mixer cavity 92 upstream from its exit. This swirling mixture enters the combustor chamber 32 where it is burned completely.
- the swirlers 110, 112, 114 may be co-swirling or counter-swirling depending on the desired turbulence and exit velocity profile of the mixer 54.
- the inner swirler 110 may be co-swirled with the pilot swirlers 70, 72 to prevent excessive interaction which would cause higher emissions at idle power settings.
- the middle swirler 112 may be co-swirled with the inner swirler 110 for the same reason.
- the outer swirler 114 may be counter-swirled to create a strong shear layer which would improve mixing and lower NOx emissions at some flame temperatures.
- the inner and outer swirlers 110, 114 would be co-swirling with the inner swirler 110 and the middle swirler 112 would be counter-swirling to create two shear layers in the main mixer cavity 92 to improve mixing and lower NOx emissions. It is envisioned that this configuration may be beneficial if the shear layer interaction between the inner and middle swirlers 110, 112 is found to have little impact on the pilot and idle performance of the main mixer 54.
- a second embodiment of the mixer 130 shown in Fig. 5, includes a main mixer 54 having an annular fuel injector, generally designated by 132, mounted between the inner main swirler 110 and the middle main swirler 112.
- the injector 132 has a port 134 at its downstream end for introducing fuel into the cavity 96 of the main mixer 54.
- the injector 132 may have a different number of ports 134 without departing from the scope of the present invention, in one embodiment the injector has 20 evenly spaced ports. It is envisioned that the fuel injector 132 may include injectors such as described in U.S. Patent No. 5,435,884.
- every other port 134 around the circumference of the injector 132 may be angled inboard and outboard (e.g., about 30 degrees) with respect to the centerline 66 of the mixer 130 as shown in Fig. 5 to enhance fuel-air mixing.
- the mixer 130 of the second embodiment is identical to the mixer 50 of the first embodiment in all other respects, it will not be described in further detail.
- pilot mixer 52 In operation, only the pilot mixer 52 is fueled during starting and low power conditions where stability and low CO/HC emissions are critical.
- the main mixer 54 is fueled during high power operation including takeoff, climb and cruise conditions.
- the fuel split between the pilot and main mixers 52, 54, respectively, is selected to provide good efficiency and low NOx emissions as is well understood by those skilled in the art.
- mixers 50, 130 described above will provide a reduction in NOx emissions of up to 70 to 80 percent during takeoff compared to 1996 International Civil Aviation Organization standards, and up to 80 to 90 percent at cruise conditions compared to currently available commercial mixers.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US675666 | 2000-09-29 | ||
US09/675,666 US6363726B1 (en) | 2000-09-29 | 2000-09-29 | Mixer having multiple swirlers |
Publications (1)
Publication Number | Publication Date |
---|---|
EP1193450A1 true EP1193450A1 (de) | 2002-04-03 |
Family
ID=24711489
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP01308241A Withdrawn EP1193450A1 (de) | 2000-09-29 | 2001-09-27 | Mischvorrichtung mit mehreren Verwirbelungsvorrichtungen |
Country Status (3)
Country | Link |
---|---|
US (1) | US6363726B1 (de) |
EP (1) | EP1193450A1 (de) |
JP (1) | JP2002168449A (de) |
Cited By (17)
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EP1262719A2 (de) * | 2001-05-31 | 2002-12-04 | General Electric Company | Verfahren und Vorrichtung zur Beherrschung der Emissionen in einer Brennkammer |
WO2003006885A1 (en) * | 2001-07-13 | 2003-01-23 | Pratt & Whitney Canada Corp. | Premixing chamber for turbine combustor |
WO2004053395A1 (de) * | 2002-12-11 | 2004-06-24 | Alstom Technology Ltd | Verfahren und vorrichtung zur verbrennung eines brennstoffs |
EP1507119A1 (de) * | 2003-08-13 | 2005-02-16 | Siemens Aktiengesellschaft | Brenner und Verfahren zum Betrieb einer Gasturbine |
EP1413830A3 (de) * | 2002-10-24 | 2006-07-26 | ROLLS-ROYCE plc | Druckluftinjektor für Kraftstoff mit verbessertem Luftverteiler und Pilot |
FR2911667A1 (fr) * | 2007-01-23 | 2008-07-25 | Snecma Sa | Systeme d'injection de carburant a double injecteur. |
WO2010042136A2 (en) | 2008-09-23 | 2010-04-15 | Siemens Energy, Inc. | Alternately swirling mains in lean premixed gas turbine combustors |
FR2957659A1 (fr) * | 2010-03-22 | 2011-09-23 | Snecma | Systeme d'injection pour chambre de combustion de turbomachine, comprenant des moyens d'injection de carburant en sortie d'une double vrille d'admission d'air |
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RU2533045C2 (ru) * | 2009-06-30 | 2014-11-20 | Сименс Акциенгезелльшафт | Горелка, в частности, для газовых турбин |
US8313046B2 (en) | 2009-08-04 | 2012-11-20 | Delavan Inc | Multi-point injector ring |
FR2957659A1 (fr) * | 2010-03-22 | 2011-09-23 | Snecma | Systeme d'injection pour chambre de combustion de turbomachine, comprenant des moyens d'injection de carburant en sortie d'une double vrille d'admission d'air |
EP2481982B1 (de) | 2011-01-26 | 2015-07-08 | United Technologies Corporation | Mischeranordnung für einen Gasturbinenmotor |
US9920932B2 (en) | 2011-01-26 | 2018-03-20 | United Technologies Corporation | Mixer assembly for a gas turbine engine |
US10718524B2 (en) | 2011-01-26 | 2020-07-21 | Raytheon Technologies Corporation | Mixer assembly for a gas turbine engine |
EP2481982B2 (de) † | 2011-01-26 | 2022-04-13 | Raytheon Technologies Corporation | Mischeranordnung für einen Gasturbinenmotor |
US8365534B2 (en) | 2011-03-15 | 2013-02-05 | General Electric Company | Gas turbine combustor having a fuel nozzle for flame anchoring |
US9500369B2 (en) | 2011-04-21 | 2016-11-22 | General Electric Company | Fuel nozzle and method for operating a combustor |
US8616471B2 (en) | 2011-05-18 | 2013-12-31 | Delavan Inc | Multipoint injectors with standard envelope characteristics |
US10480472B2 (en) | 2012-02-16 | 2019-11-19 | Delavan Inc. | Variable angle multi-point injection |
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US6363726B1 (en) | 2002-04-02 |
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